一种高负荷叶型优化设计方法

A method of optimal design of highly-loaded airfoil

采用3段3次贝塞尔曲线拟合叶型中弧线弯角分布,两段3次贝塞尔曲线拟合厚度分布,进行流线面造型,并结合优化算法进行寻优.S1流场评价工具为MISES软件,寻优算法为遗传算法(GA).将传统遗传算法进行改进,引入并行模块,较大程度地提高了计算效率.实现了高负荷叶型的自动优化,探讨了高负荷叶型的设计准则,并将准则应用于超声叶型设计.结果表明:相比于原始叶型,优化后的叶型Ⅰ在总压损失系数略降低和出口气流角不变的条件下,可用攻角范围拓宽约2°,叶型Ⅱ的总压损失系数明显降低,可用攻角范围拓宽约0.6°,落后角降低约3.9°.

3-section of cubic Bezier spline was used to fit the tangent of camber line 2-section of cubic Bezier spline was used to fit the thickness distribution. The airfoil built on streamline-surface. S1 flow field was evaluated by MISES software and optimiza algorithm was performed by genetic algorithm （GA）. By introducing a parallel mode to and was tlon the traditional GA, computational efficiency was improved considerably. Automatic design and optimization of highly-loaded airfoil was achieved and the design criteria of highly-loaded airfoil for design of supersonic airfoil were investigated. Results show that compared with the original airfoil, incident angle range of airfoil I is broadened about 2 degree under the premise that loss coefficient of total pressure reduces a little and the airflow angle of outlet is unchanged; if loss coefficient of total pressure of airfoil II obviously reduces, incident angle range is broadened about 0.6 degree and deviation angle reduces about 3.9 degree.